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Molly Kane January 17, 2008 Interface Structures, Aero- and Thermo-Loading Nose Cone Materials

Molly Kane January 17, 2008 Interface Structures, Aero- and Thermo-Loading Nose Cone Materials. Sizing. Size of nose cone based on historical data from Vanguard rocket. L total – 12.64 m Radius – 0.3344 m L nose_cone – 1.071 m Surface Area – 1.178 m. Structures. Materials.

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Molly Kane January 17, 2008 Interface Structures, Aero- and Thermo-Loading Nose Cone Materials

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  1. Molly KaneJanuary 17, 2008Interface Structures, Aero- and Thermo-LoadingNose Cone Materials AAE 450 Spring 2008

  2. Sizing • Size of nose cone based on historical data from Vanguard rocket • Ltotal – 12.64 m • Radius – 0.3344 m • Lnose_cone – 1.071 m • Surface Area – 1.178 m AAE 450 Spring 2008 Structures

  3. Materials • Aluminum – low heat applications, relatively inexpensive • Titanium – strong, high temperature usage • Magnesium Alloys – low density, low heat applications • Molybdenum – very high heat capabilities, maintains strength • Carbon-Carbon – ceramic, light, very expensive • Hafnium Diboride – ceramic, light, very high heat capabilities Future Work • Ceramics, combinations of materials, aero-thermal implications, pricing AAE 450 Spring 2008 Structures

  4. Backup Slides AAE 450 Spring 2008 Structures

  5. References Anonymous, “Titanium, Commercially Pure”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Anonymous, “Magnesium, Mg-6Al-1Zn”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Anonymous, “Aluminum, Al-2.5Mg-0.25Cr”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Anonymous, “Carbon-Carbon Composite Thermal Protection System for Spacecraft from NextTechs Technologies,” NextTechs Technology c. 2000-2008, [http://www.azom.com/details.asp?ArticleID=3904. Accessed 1/16/08] Buckman, R.W., “Molybdenum, Commercially Pure”, Aerospace Structural Metals Handbook, Setlak/CINDAS, West Lafayette, IN, 2002. Ewig, R. Sandhu, J. Shell, C.A., Schneider, M.A., Bloom, J.B., Ohno, S., “The K2X: Design of a 2nd Generation Reusable Launch Vehicle,” 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Huntsville, AL, 2000, pp. 11-12. Klemans, B., “The Vanguard Satellite Launching Vehicle” The Martin Company, Engineering Report No. 11022, April 1960. AAE 450 Spring 2008 Structures

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